Control mechanism for aeroplanes



9 H. M. SALISBURY ET AL 14718.70]

CONTROL MECHANISM FOR AERQPLANES Filed Feb.. 11

[ r 449 ATTORNEYS.

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Patented June 25, 1929.

UNITED STATES 1,718,707 PATENT OFFICE.

HERVEY M. SALISBURY, F WALNUT GROVE, AND AR'IKUR E. MILLER, 01 SACRAMENTO, CALIFORNIA.

CONTROL MECHANISM FOR AEROPLANES.

Application filed February 11, 1928. Serial No. 253,612.

This invention relates to a control mechanism for aeroplanes and especially to a mechanism whereby the landing speed of a plane may be considerably retarded.

The object of the present invention is to provide a control mechanism for aeroplanes, the primary function of which is that of an air brake to enable the operator to slow down the plane when making a landing. Other objects are to provide a control mechanisin which will facilitate steering, turn.- ing and rising when taking off and which will retard sieed when diving into a land- The invention is shown by way of illustration in the accompanying drawings in which:

Fig. 1 is a front iew of an aeroplane, said view l eing partially in section,

Fig. 2 is an enlarged cross-section of the fuselage, showing the position of the control. levers,

Fig. 3 is a partial longitudinal section taken on line IIIIII, Fig. 2,

Fig. 4. is a diagrammatic plan view of the control levers and the vanes actuated thereby.

In the drawings a monoplane type of plane is illustrated in which A indicates the fuselage or body of a plane, B the wings, G the running gear, and D the struts whereby the wings are braced with relation to the fuselage and running gear. The struts D are turned to the air stream with their greatest width at right angles to the stream so as to avoid as little head resistance as possible and they are disposed on an angle with rela tion to the wings B so that triangularshaped spaces are formed on opposite sides of the fuselage. These spaces contain the control mechanism forming the subject matfor of the present application. The mechanism consists of triangular-shaped frames lil and F. each frame consisting of an upper lmrizonlal section 2. an inner vertical section 3 and an inclined bottom section 4 which is disposed substantially parallel with the struts D. Extending; crosswise of the fuselage are arms 5 to which are secured hanger brackets or journals 6. Journalled in the respective brackets are shafts 7 and 8. The outer ends of the shafts are secured to the inner vertical sections 3 of the frames E and F and support the same. The outer ends of the frames are also provided with shaft members, such as indicated at 9 and 10.

These shaft members align with the shafts 7 and 8, and they are jou nailed in bearing brackets 11 and 12 supported by the struts. The several shafts form pivots which permit the frames to be turned to assume the vertical position shown in Fig. 1 or to a horizontal or any intermediate position desired, the positions assumed being controlled by levers 13 and 14 secured on the inner ends of the respective shafts 7 and 8, as shown in Figs. 1 and 2. The levers are secured to the inner ends of the shafts 7 and S and segmental rack bars 13 and 1% are secured to the arms 5. Each lever provided with a pawl 15 and the actuating grip 16, and the shafts and the frames may, accordingly, be secured in any position desired.

Extending crosswise of the frames and journalcd in the sections 2 and 4 are a series of rods or shafts l7. Secured upon eacl rod is a vane 18 and attached to the outer edges of the vanes are cables or ropes 19, the inner ends of which are secured at opposite ends, as indicated at 20 and 21, tolevers 22 which are pivotally secured as at 23 on the respective shafts 7 and 8.- These lovers are also provided with pawls and gri s as indicated at 2 1 and they cooperate with segmental racl; bars 25 so that the lovers may be locked in any position desired. By swing ing the levers 22 about their pivots 23, movement is imparted through the cables 19 to swing the vanes so that they will close or open, as shown in It should be noted that each set of vanes is controlled by separate levers so that the *anes in one frame may be closed or partially open and vice versa, independently of the vanes in the opposite frame. It should also be noted that the frames are in turn independently con trolled by the levers 13 and 1% and that each may. accordingly, be independently controlled. The sevcral lovers are disposed within convenient reach of the operatm' and as such may be quickly manipulated whenever required.

The purpose of the control mecluinism is to provide a suitable brake for aeroplanes, i. e., a brake that will enable the operator to slow down the aeroplane when making a landing and without affecting the trim of the plane. The beams of an aeroplane wing are, in most cases. so situated that the center of pressure of the wing is midway be tween them. As the center of pressure and with brakes on or off.

A number of uses of a control mechansm, such as here illustrated, are to be seen at once. It will not only retard the speed when making a landing but it will allow a machine to dive into a landing, rather than to glide, without picking up dangerous speed, the plane being at the same time under perfect control. The control mechanism may be used in conjunction with the rudder to facilitate steering and rapid turning. It may be employed when taking off to assist in rising by turning the frames to a horizontal or substantially horizontal position, and it may also be utilized to impart a side slip or lateral motion to a plane when in forward flight, this being of considerable importance particularly in warfare.

While the control mechanism is illust ated as attached to a monoplane type, it is obvious that it may be used in conjunction with biplanes or the like, and while some of the features of the present invention are more or less specifically described and illustrated, we wish it understood that various changes may be resorted to within the scope of the appended claims; similarly, that the materials and finishes of the several parts employed may be such as the manufacturer may decide or varying conditions or uses may demand.

Having thus described our invention, what we claim and desire to secure by Letters Pat ent is: v

1. The combination With the wings and fuselage of an aeroplane, of a pair of elongated frames disposed one on each side of the fuselage and adjacent the wings, means permittitng pivotal movement of each frame on the longitudinal axis drawn therethrough, a plurality of vanes pivotally mounted crosswise of each frame, and means for imparting movement to the vanes about their pivots.

E2. The combination with the wings and fuselage of an aeroplane, of a pair of elongated frames disposed one on each side of the fuselage adjacent the wings, a pair of shafts one for each frame and aligning with the longitudinal axis of the frames, means socuring the frames to said shafts, manually actuated means for rotating the shafts and the frames from a vertical to a horizontal position, means for locking the shafts and the frames in a horizontal or vertical or any intermediate position, a plurality of vanes pivotally supported in each frame and crosswise thereof, and means for swinging the vanes about their pivotal points and for securing them in any adjusted position,

The combination with the wings and fuselage of an aeroplane, of a pair of elongated frames disposed one on each side of the fuselage adjacent the wings, a shaft attached to the inner end of each frame in alignment with the longitudinal axis thereof, journal members supporting the shafts in the inner ends of the frames, pivotal supportp' aligning with the shafts and disposed at the outer ends of the frames, a lever secured to each shaft, locking means cooperating with each lover, a second lever one for each shaft, said levers being pivotally supported by their respective shafts, locking means on each shaft with which said levers are engageable, and a plurality of pivotally mounted vanes in each frame and actuated by the pivotally mounted levers.

41-. In a device of the character described, a pair of elongated frames disposed one on each side of the fuselage in an aeroplane and adjacent the wings thcrcof, a pivotal support for each frame and parallel with the wines, lllOkllli-l for rotating each frame independently of the other from a vertical to a horizontal position, means for locking the frames in the horizontal or vertical position or in any intermediate position, a plurality of pivotally mounted vanes extending crosswise of each toe. and independent means for each set of vanes for rotating them about their pivotal points.

In an acropiane of the character described, a monoplane wing, a fuselage disposed centrally thereof, a pair of struts angularly disposed one on each sine of the fuselage and connected to the wings, a pair of triai guar-shaped frames disposed one on each side of the fuselage between the win and the struts, a pivotal support for each end of each frame, a plurality of vanes pivotally mounted crosswise of each frame, means for swinging the vanes in ea ch frame about their pivots independently of each other, and means for swin ine each frame about its pivotal. support.

6. In an aeroplane of the character described, a monoplane wing, a fuselage disposed centrally thereof, a pair of struts angularly disposed one on each side of the lage and connected to the wings, a pair of triangular-shaped frames disposed one on each side of the fuselage between the wings and the struts, a pivotal support for each end of each frame, a plurality of vanes pivotally mounted (rust--1- wise of each frame, and at righhangies to the pivotal supports for the frame. means for rotating each frame about its pivotal support from a horizontal to a vertical position and independently of each other. means for locking each f 'amc against rotation about its pivo support. whether in a vertical. a horizontal or an intermediate position, means for imparting movement to the vanes about their pivotal supports, and means for locking the vanes against movement about their pivotal supports hen adjusted.

HERVEY M. SQLFSBITBY.

AR THUR E. BUTLER.

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